Orifice control means for jet propulsion motors



May l, l951 J. HALTENBERGER 2,551,372

ORIFICE CONTROL MEANS FOR JET PROPUL'SION MOTORS Filed NOV. 13, 1945 Y'i' Y l5 ao ,Byyull A l 78 T! I s" 64 15 gli '19 76 Y ATTORNEY PatentedMay l, 1951 UNITED 2.5551372 ommen coN'rnoL MEANs Fon JET @polimi-'SIONMomons Jules Haltenberger, lLa Jolla, .Qalif., assignor .to ConsolidatedYuleeAircraft Corporation', San Diego, Calif., a '.corporationoffDelaware' Application 'November13, 19.45, .Serial N0. .62,8,139

Y9 QC'laims. ,(Cl. 60135.55)

This invention relates to jetpropu'lsion'motors andmore particularly to.jet orice control means.

An object of Athis invention is .to provide :an improved form of orifice.control for a.;jet propulsion motor while maintaining .a .constantdirection thrust flow.

A further object of this invention is to1p1ovide a disappearing thrustflowspoiler `for a .jet propulsion motor.

A further object of this invention is to provide an adjustable controlkmeans for a jet propulsion motor `which serves as an orifice controlmeans while in one position, and as a thrust flow spoiler means inanother position.

A further object of this invention is to provide thrust ilow spoilercontrol means which in normal operation is withits actuating elements,outside of the path of the thrust flow.

A further object of this `in ventionis to provide an improved formofvorice control means Vfor a jet propulsion `motor which embodies .anvautomatic altituderesponding vdevice and means for overriding suchdevice.

A further object of this invention is -to yprovide in a jet propulsionmotor improved :.meansfor controlling the direction of the Athrust llow.

Other objects and features of this inventioll-.Will be readily apparentto those skilled in the art from the following specification andappended drawing illustrating certain ypreferred v embodiments in which:

AFigure 1 is a longitudinal view-in cross section of 'an vaeroplane Ajetpropulsion motor .according to the presentinvention. Y

Figure 2 is an enlarged-view, partiallyfinfsection, of the rear end ofthe jet propulsion motor shown in Figure 1, and illustrating thejet-controlling. elements and operating means thereof.

Figure 3 is an end elevational view ofFigure 2 with certain of theoperating meansomitted.

Figure 4 is a modification of the operating means of ,Figure 2.

Figure 5 is a modication of lthejetcontrolling means of Figures l, 2,and 3.

Figure 6 illustrates a jet controlling means similar to that in Figure5, but including jjetdirectional control.

Figure '7 is a further modificationof the invention.

VJet propulsion motors are providedwithfmanually operated thrustcontrolling means to reduce the speed of the plane for landing, these`means operate to reduce the speed by reducing the combustion fuel flowVas by a valve and 'thereby the revolutions of thecompressor and turbineand respectively. Should, howevenlthe pilot be forced to reascendimmediately to avoid anobstruction on the field, or through overshooting:the ield, or similar causes, the reopening of the combustion fuel valve4will not immediately increase the thrust, but. rather, there is a lapse.Q f Atime until 2 the lmotor .reaches the desi-red high revolutionstoinsure suiiicient highthrust `toeilect the Aoperation properly.

-It has-been Lproposed to maintain the .high revolution-.of the'motorandthe high thrust even While landing and .to provide spoiling means,riemotelyoperated, which act to destroy the thrust effect gf the motorto permit landing; by displacing, .-orreturning .to its originalpositon,the spoilingv `device the ,high desired thrust becomes instaneouslyavailable for re-takeol.

O f 4allspoiling devices that Ia-m aware of, such spoilers in normaloperation obstructed thethrust iiow and Vwake thereof `and reduced theeliiciency of the motor, such obstructions besides being ,in-

. efficient entail the `dangerof being burned away because their normalposition lies in thefhot thrust flowarea It is here proposedto provide aspoilerdevice which when retracted is normally out of the. path of thethrust ow area, and in the preferred forms to use such spoiler deviceasa meanstocontrol the jet orice size.

Varying the. jet .propellermotorthrust orifice vis not new 4per se,`:but .the constructions .that-I am yaware of were disposed in the ow ofthe thrust stream. Itis here Iproposed to provide oriiice sizecontrolling .means without obstructing such now.

.Referringto Figures 1,2 and 3 it will be seen that ,a jetpropulsionmotor, generally at I0, is provided with a .usual vair ,passage inhousing II supplying .air toa usual compressor inhousing I:2,;combustionchambers in housings I3 leading to ausual turbine Vin the large end ofhousing I4, ireferredto in the lart as the tail cone, and tail pipe I5provided-with a jet orifice at'theend of suchpipejn domes I6; operatingmeans, gen erally at I1, complete theusual ,well known jet propulsionmotor.

`It will be .seen from. Figure l that the jet propulsion motongenerallyat Ill, is encasedrin an aerodynamically shaped housing Il having Vausual air -inlet ,passage I8. The housing YITI `is supported by anaeroplane wing, generally at It. Themotor housing I'I is also `providedwith a tail cone. shroud 20, anda tail pipe shroud 2l terminatinginshroud `orifice wall 22, :with the thrust j etandwake 23thereofillustrated in chain lines.

As isolear from Figures 2 and 3 the tailpipe I5 and dome formations I6respectively end in w all I.Iil and .serve as a housing for apairofradially displaceable crescent shaped orifice control ielements 2 5` and26, formingsubstantially a AWall when inretracted position. Theseelements 2 5 and. 26 are provided lwith sealing partrings 2 4 at theirouter ends arrangedto slide on the inner surfaces of upper and 'lower,domes I6,

and eachisprovided-with ua metering half oiganV orifice 27, here, yinits normal` positionindicated bysolid lines inFigure, forming a circularyaperture A6 0 I lisellfic with .tail ,pipe I5.. `It, will be noted thatthe element 25 is provided with a lata lateral protruding wall 29. Thesewalls 28 and 4 29 are provided to increase the spoiler effect (to behereinafter described).

As shown in Figure 3 orifice controlelement 25 is secured as by a shearpin 361:0 a shaft 3| passing through the tail pipe I5, and theshavft 3|,as by a shear pin 32, is connected to an actuating lever 33. The oricecontrol element 26 is in a similar manner connected to an operatinglever 34. Y

The element 25 is provided with a hinge eye 251 and the element 26 withhinge eye 261. It is `important to note that these eyes serve merely .ashinge bearings on their associated shafts 3| respectively. y

Operating levers 33 and 34 are connected as by :rods 35 to a control nut36 at the outer ends of the lateral extensions 3l thereof. Control nut.36 travels on a threaded shaft 46, an extension lof a usual armature ofa usual two-directional yelectric motor 4|, which motor is positioned onand secured to the tail pipe I5 as by bracket ll|1 in close proximity tothe jet orifice to diminish errors brought about by tail pipe heatlongitudinal expansion.

The control of the two-directional motor 4| is schematically illustratedin Figure 2 and embodies the well known elements of a remotelypositioned control potentiometer in housing 42, its manual operatinglever 45, a sensitive relay in housing 44, an actuated potentiometer inhousing 45, located adjacent to the motor 4|, limiting link elements 46and 47, extending from housing 45 to nut 36, and an electrical source58, whichY may be a battery, and suitable wire connections between theseelements and the remotely positioned control potentiometer complete thejet orifice control actuating mechanism.

As it is clear from Figure 3, orice control elements 25 and 26 are shownin chain lines in various positions. When both elements 25 and 26 areretracted or disposed forwardly of the end of the tail pipe I5 and domesI6 their halforifices 21 will assume a new position, indicated by thechain line 50. As it is clear from Figures 2 and 3 the projection of thehalf-orifices 2l in this new position will have a reduced crosssectional area, and as here illustrated forms the minimum jet orifice.The vertical position of elements 25 and 26 as illustrated in Figures 2and 3 form the maximum opening of the jet orice. It is well understoodthat the elements 25 and 26 can occupy any intermediate position betweenthe two positions described above, the positions of the elements 25 and26 being determined by ythe movement of the manual operating lever 43.

When elements 25 and 2'6 are extended to the rear of wall |61, andpreferably to chain line indicated position 5|, they will act as aspoiler. To further increase their eiectiveness in spoiling the thrustjet the protruding walls 28 and 29 have -been provided.

Figure 4 illustrates a housed potentiometer 421. Here however, theactuating mechanism for the potentiometer includes an altituderesponsive device, such as a Sylphon barometer 55 interposed betweenpotentiometer control lever 531 and a manual operating lever 56. rIhelever 56 has an extension 51 beyond the fulcrum pin 58, which extensioncontains a plunger 59 and spring 60 and arranged to yieldingly engageteeth 6| on sectorY 62 integral with housing 421. In this arrangementthe control-1ever'56 is held in normal engagement by plunger 59 andteeth 6|, whereas the barometer with changes in altitude will n controlthe potentiometer to vary automatically the jet orifice of the jet motorin response thereto. As it is clear from Figure 4, this barometriccontrol can at any time be overridden manually by the pilot.

I The above describes my invention for the applications where it ispreferred to provide an orifice without decreasing or converging thedefining walls of ,the tail pipe section carrying the adjustable,orifice. When a converging tail pipe andadjustable orifice is desiredthis is illustrated in Figure 5. -I-Iere tail pipe l51 is provided withpartially ball-shaped, vertically disposed terminations 63, and arcuate'lateral extensions 64 (only one of which is shown) which project fromthe outer end of tail pipe |51 and are continuations of the wallsthereof.

The tail pipe |51 is provided with fulcrum pins 3| 1, and hingedlymounted thereon are a pair of partially ball-shaped crescent sectors 65and 65. The forward end of each sector is provided with a channel 6lcontaining a sealing ring 68, comprised of such material as asbestos orIconite Each sector y65 and 65 is provided with a lug 16, operativelyconnected to links 351 which in turn are operatively connected tocontrol nut 361 on threaded shaft 461, an extension of the armature ofthe two-directional motor 4|1. The operation of the motor M1 is the sameas the operation of motor 4| which was described in connection withFigures 1, 2, 3, and 4 and it is believed it need not be describedagain.

Here, however, Figure 5 illustrates an orice control mechanism which ismounted on the outside of the tail pipe in contrast to the structuredescribed in Figures l, 2, and 3. It will be also noted that therestriction ci the jet orice is disposed in the direction of the spoilerposition (indicated with chain lines generally at 7|) whereas in Figure3 the restriction is obtained by tilting or moving the orice elementsaway from the spoiler position.

As it is clear from Figures l, 2, 3 and 5 the mechanism operating theorifice elements is arranged with particular attention paid tosynchronous movement of the elements to maintain a concentric jetdirectional iiow while in therextended or spoiler position, small orlarge orice position or in any size oriiice position therebetween. f y

When it is desired to divert the jet flow in a substantially verticalplane to assist in quick subf stantially vertical maneuvering of theplane, or

in such emergencies as where the tail surface has been damaged, amodication Yof the invention to accomplish this is illustrated in Figure6, here shown as being similar to Figure 5, and it is believed that onlythe vertical control means to effect diversion of the jet ilow need bedescribed to avoid repetition. The two-directional motor 4|1 here issupported on a cradle 75, fulcrumed on pin 37|1 as by an eyelet 'I6forming the sponse in ganingror losingaltitude in an .emer-.'

gency, asy an example, when being pursued or attacked by an enemy plane,such quick maneuvering will present a diiiicult target to the enemy.

When it is desired to use a iixed orifice jet and to provide same withsynchronously acting spoiler elements, a modification as illustrated inFigure 7 is utilized. Here tail pipe I5 terminates in a conicalextension S5. The rear portion thereof is provided with a fulcrumbearing 85 supporting a pair of substantially semi-cylindrical shapedspoiler elements 8l and S8 which elements are operated by links 89 and anut 96 which moves on the threaded extension 9| of the armature of atwo-directional motor 4l. Chain lines, generally at 92, indicate theextended position of the spoiler elements 81 and S8, set for activespoiling. Upon fast operation of the extension of the spoiler elements,jet orifice area reduction is substantially eliminated. In slowoperation of the spoiler elements this modification of the invention canbe used for restriction of the jet orifice.

Figures l, 2, and 3 illustrate a wall type jet orifice. Figures 5, 6,and 7 illustrate a generally converging jet orifice. Each of themodifications illustrated, however, utilizes adjustable orifice elementswhich when extended form a spoiler.

While certain preferred embodiments of the invention have beenspecifically disclosed, itis understood that the invention is notlimited thereto as many variations will be readily apparent to thoseskilled in the art and the invention is to be given its broadestpossible interpretation within the terms of the following claims.

I claim:

1. In a jet propulsion motor having a jet orice, movable spoiler meanspositioned adjacent said jet orice and movable in a first direction forvarying the size of the jet orifice and movable in a second direction toa jet spoiling position, a reversible motor, means operativelyinterconnecting said motor and said movable spoiler means for movementof said latter means, and remotely positioned control means havingoperative connection with said reversible motor for actuation thereof.

2. In a jet propulsion motor having a jet orifice, movable spoiler meanspositioned adjacent said jet orifice movable inwardly of the jetpropulsion motor for varying the size of the jet orifice and movableexteriorly of the jet propulsion motor to a jet spoiling position, areversible electric motor, means operatively interconnecting said motorand said movable spoiler means for movement of said latter means, andremotely positioned control means for electrically controlling theactuation of said electric motor.

3. In a jet propulsion motor having a jet orifice, movablecrescent-shaped means positioned adjacent said jet orifice movable in arst direction for varying the size of the jet orifice and movable in asecond direction to a jet spoiling position. a lateral projecting Wallmember on each of said crescent-shaped means, which Wall members aremovable toward one another to provide a spoiling effect, and remotecontrol means operatively associated with said movable crescent-shapedmeans for actuation thereof.

4. In a jet propulsion motor, a tail pipe terminating in an opening,movable crescent-shaped means positioned within said tail pipe adjacentsaid opening and movable inwardly into said tail pipe for varying thesize of said opening and movable in the opposite direction to a jetspoiling position exteriorly of said tail pipe, and remote control meansoperatively associated with said movable crescent-shaped means foractuation thereof.

5. In a jet propulsion motor, a tail pipe terminating in an opening,movable crescent-shaped means positioned within said tail pipe adjacentsaid opening and movable inwardly into said tail pipe for varying thesize of said opening and movable in the opposite direction to a jetspoiling position exteriorly of said tail pipe, a lateral projectingwall member on each of said crescentshaped means, which wall members aremovable toward one another to provide a spoiling effect, and remotecontrol means operatively associated with said movable crescent-shapedmeans for actuation thereof.

6. In a jet propulsion motor, a tail pipe terminating in a jet orifice,dome formations provided on said tail pipe adjacent the end thereof,crescent-shaped means movably positioned within said tail pipe andextending into said dome formations, and ,remote control means formoving said crescent-shaped means inwardly in said tail pipe for varyingthe size of the jet orifice and for moving said crescent-shaped means inthe opposite direction to a jet spoiling position exterior- 1y of saidtail pipe.

7. In a jet propulsion motor, a tail pipe terminating in a jet orice,dome formations provided on said tail pipe adjacent the end thereof,crescent-shaped means movably positioned within said tail pipe adjacentsaid jet orifice and extending into said dome formations, remote controlmeans operatively connected to said crescentshaped means for movementthereof inwardly into the tail pipe to vary the size of the jet orificeand for movement thereof in the opposite direction to a jet spoilingposition exteriorly of the tail pipe, and a lateral projecting wallmember on each of said crescent-shaped members, which wall members aremovable toward one another to provide a spoiling effect.

8. In a jet propulsion motor, a tail pipe, walllike jet orificecontrolling elements in association with said pipe and adapted to serveas spoilers, lateral wall protrusions provided on each of said elementsin positions normally lying outside of said jet stream, and means tooperate said elements into jet spoiling position wherein said lateralwall protrusions extend into the jet stream to augment the spoilingeffect of said elements.

9. in a jet propulsion motor having a variable iet orifice, movabiecrescent-shaped means positioned adjacent said jet orifice forcontrolling the site of said orice when moved in one direction and meansoperatively associated with said crescent-shaped moans to move saidcrescent- Shaped means in the opposite direction whereby saidcrescent-shaped means will operate as a spoiler.

JULES HALTENBERGER.

REFERENCES CITED foilown. references are of record in the le of thispatent:

UNITED STATES PATENTS Number Name Date 340,237 Nagel et al Apr. '20,1886 1,493,280 Rees May 6, 1924 1,560,642 Barbarou Nov. 10, 19251,572,812 Rees Feb. 9, 1926 2,390,161 Mercier Dec. 4, 1945

